WO2012166625A1 - Turbine à aubes de rotor irrégulièrement chargées - Google Patents

Turbine à aubes de rotor irrégulièrement chargées Download PDF

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Publication number
WO2012166625A1
WO2012166625A1 PCT/US2012/039644 US2012039644W WO2012166625A1 WO 2012166625 A1 WO2012166625 A1 WO 2012166625A1 US 2012039644 W US2012039644 W US 2012039644W WO 2012166625 A1 WO2012166625 A1 WO 2012166625A1
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WO
WIPO (PCT)
Prior art keywords
blade
rotor
turbine
region
flow rate
Prior art date
Application number
PCT/US2012/039644
Other languages
English (en)
Inventor
Walter M. Presz
Michael J. Werle
Robert Dold
Timothy Hickey
Original Assignee
Flodesign Wind Turbine Corp.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Flodesign Wind Turbine Corp. filed Critical Flodesign Wind Turbine Corp.
Priority to CA2834595A priority Critical patent/CA2834595A1/fr
Priority to EP12726977.7A priority patent/EP2715119A1/fr
Publication of WO2012166625A1 publication Critical patent/WO2012166625A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/0608—Rotors characterised by their aerodynamic shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03B—MACHINES OR ENGINES FOR LIQUIDS
    • F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
    • F03B3/12—Blades; Blade-carrying rotors
    • F03B3/126—Rotors for essentially axial flow, e.g. for propeller turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/04—Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2210/00—Working fluid
    • F05B2210/16—Air or water being indistinctly used as working fluid, i.e. the machine can work equally with air or water without any modification
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/13—Stators to collect or cause flow towards or away from turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/13—Stators to collect or cause flow towards or away from turbines
    • F05B2240/133—Stators to collect or cause flow towards or away from turbines with a convergent-divergent guiding structure, e.g. a Venturi conduit
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/20—Hydro energy
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Definitions

  • the present disclosure relates to turbine rotor blades of a particular structure, and to shrouded turbines incorporating such blades. More specifically, the present rotor blade design comprises uneven loading (also known as “asymmetrical loading” or “unbalanced loading”).
  • HAWTs Horizontal axis turbines
  • a conventional HAWT blade is commonly designed to provide substantially even blade loading across a power-extracting region of the blade.
  • One common mathematical tool for predicting and evaluating blade performance is blade element theory (BET). BET treats a blade as a set of component elements (also known as "stations"). Each component element may be defined by a radial cross section of the blade (known as an airfoil) at a radial position (r) relative to the axis of rotation and width of the element (dr).
  • a conventional HAWT blade may also include one or more non-power-extracting regions.
  • conventional HAWT blades are often tapered at the tip and/or root of the blade, for example, to reduce vortices. Such tapered regions or otherwise minimally loaded regions proximal to the tip and/or root of the blade are considered non-power-extracting regions for the purposes of the present disclosure.
  • Parameters which may be adjusted to ensure even loading for different mass flow rates include pitch (also known as the "angle of attack") and/or airfoil shape, for example, characterized by chord length, maximum thickness (sometimes expressed as a percentage of cord length), mean camber line, and/or the like. Airfoils for a conventional evenly loaded HAWT blade typically exhibit longer chord lengths and greater pitch toward the root than toward the tip to account for a higher mass flow rate toward the tip (note that for conventional unshrouded HAWTs, there is little difference between fluid velocity at the center of the rotor plane and fluid velocity at the perimeter of the rotor plane.
  • the present disclosure relates to novel turbine blade designs characterized by uneven blade loading.
  • the present disclosure further relates to systems and methods for utilizing and methods for manufacturing unevenly loaded turbine blades.
  • Uneven blade loading teaches away from the norm of the industry and is particularly useful for taking advantage of non-uniform flow profiles, e.g. such as may be created by a shroud.
  • unevenly loaded blades may provide particular advantages, for example, greater power extraction and/or greater efficiency relative to conventional evenly loaded blades particularly in a shrouded turbine environment or in other turbine environments where fluid flow velocity is non uniform across the rotor plane.
  • An embodiment includes a shrouded axial flow fluid turbine including an aerodynamically contoured turbine shroud having an inlet and configured to produce a non-uniform fluid velocity profile across a rotor plane when exposed to a fluid flow.
  • the fluid turbine also includes a rotor disposed downstream of the inlet and configured to extract energy from fluid passing through the rotor plane.
  • the rotor includes a central hub and a plurality of blades, with each blade including a root region having a blade root, a tip region having a blade tip, a mid-region disposed between the root region and the tip region, and a blade axis extending radially from the blade root to the blade tip.
  • Each blade is configured to have a value of power extraction per mass flow rate at a radial position along the blade axis that is greater at a first radius in the tip region of the blade than at second radius in the mid-region of the blade when exposed to the nonuniform fluid velocity profile.
  • Another embodiment includes a rotor configured for use with a shrouded fluid turbine having a turbine shroud that creates a non-uniform fluid velocity profile across a rotor plane when exposed to a fluid flow.
  • the rotor includes a central hub with a central axis of rotation and one or more rotor blades.
  • Each each of the one or more rotor blades includes a root region having a blade root that couples with the central hub, a tip region having a blade tip, a mid-region disposed between the root region and the tip region, and a blade axis extending from the blade root to the blade tip.
  • a pitch of the blade as a function of radial position along the blade axis is configured to, when connected with the central hub, produce a power extraction per mass flow rate that is greater at a first radius in the tip region of the blade than at second radius in the mid-region of the blade when exposed to the non-uniform fluid velocity profile.
  • An embodiment includes a method of operating a shrouded axial flow fluid turbine including an aerodynamically contoured turbine shroud having an inlet, and a rotor disposed downstream of the turbine shroud inlet.
  • the rotor includes a plurality of blades with each blade having a root region including a blade root, a tip region including a blade tip, and a mid-region disposed between the root region and the tip region.
  • the method includes establishing a non-uniform fluid flow through a rotor plane in which an average velocity of fluid flowing through an area of the rotor plane associated with the tip region of each blade is greater than an average velocity of fluid flowing through an area of the rotor plane associated with the mid-region of each blade.
  • the method also includes extracting power from the non-uniform fluid flow using the plurality of blades by extracting a greater average power per mass flow rate over the tip region of each blade than an average power per mass flow rate extracted over the a mid-region of each blade.
  • an unevenly loaded turbine blade including a power-extracting region adapted for radially- varied (relative to the axis of rotation) power extraction per mass flow rate. More particularly, the pitch and/or shape of the airfoil at a first radial position may be configured, so that the power extraction per mass flow rate of the blade at the first radial position is different than the power extraction per mass flow rate of the blade at a second radial position.
  • the power-extracting region may be configured to take advantage of a non-uniform flow profile, for example, a flow profile where flow velocity is expected to be greater at a first radial position than at a second radial position.
  • the power-extracting region may be configured such that power extraction per mass flow rate at the first radial position is greater than power extraction per mass flow rate at the second radial position.
  • the power-extracting region may optimized for an expected relative flow velocity between fluid flow at a first radial position and fluid flow at a second radial position.
  • the power-extracting region may optimized based on optimal lift/drag ratios for each radial position such as a maximal lift/drag ratio prior to stall or prior to a selected safety threshold.
  • the greater the flow velocity at a radial position the greater the optimal lift/drag ratio at that position and the greater the power extraction per mass flow rate at that position.
  • relative flow velocity between two radial positions may be related, for example, proportional to relative power extraction per mass flow rate between the two radial positions.
  • Another example embodiment relates in general to turbine environments wherein fluid flow velocity is non-uniform across the rotor plane.
  • a turbine may include at least one shroud that is in close proximity to or surrounds at least a portion of a rotor and affects a non-uniform flow profile.
  • shroud that is in close proximity to or surrounds at least a portion of a rotor and affects a non-uniform flow profile.
  • a shrouded turbine is a mixer-ejector turbine in which an ejector shroud may be in close proximity to or surround an exit of a turbine shroud. It will be appreciated that embodiments of unevenly loaded blades as described herein may be incorporated into to the design of the rotor of the mixer-ejector turbine.
  • the turbine shroud may include a set of mixing lobes along the trailing edge that are in fluid communication with the inlet of the ejector shroud. Together, the mixer lobes and the ejector shroud may form a mixer-ejector pump that provides a means of energizing the wake behind the rotor plane.
  • the mixer-ejector pump may further provides increased fluid velocity near the inlet of the turbine shroud, at the cross sectional area of the perimeter of the rotor plane.
  • the power coefficient of the mixer-ejector wind turbine may be between approximately 1.2 and 2.0.
  • the power output is derived from the rated fluid velocity and rotor area and results in a given average total pressure drop across the rotor plane.
  • the total pressure is represented by:
  • AI> 1 2 ⁇ - V -' - f
  • AP T is the change in total pressure between the upstream and downstream sides of the rotor plane
  • p is the density of the fluid in the stream
  • V w is the free stream fluid speed
  • V a is the accelerated velocity through the rotor
  • CP is the coefficient of power
  • a mixer ejector turbine uses a mixer/ejector pump in combination with highly cambered ringed airfoils to improve turbine efficiency.
  • Two factors which may be important for optimal blade design for the MET system include the speed up of the flow at the rotor station and/or the energy addition to the rotor wake flow in the mixer/ejector.
  • the one-dimensional control volume power predictions (above) account for and utilize both of these effects.
  • the cambered shrouds and ejector bring more flow through the rotor allowing more energy extraction just due to higher flow rates.
  • the mixer/ejector transfers energy from the bypass flow to the rotor wake flow allowing higher energy per unit mass flow rate through the rotor.
  • a MET in accordance with one embodiment provides increased fluid flow velocity at the perimeter region of the rotor plane relative to the fluid flow velocity at a center region of the rotor plane.
  • An unevenly loaded blade, as described herein may be designed to accommodate more energy extraction per unit mass flow rate at the perimeter region and less energy extraction per unit mass flow rate at the center region of the rotor plane.
  • an unevenly loaded blade, as described herein is better suited than a conventional symmetrically loaded blade to maximize power extraction from fluid with a non-uniform flow velocity.
  • Figure 1 is a front right perspective view of an example horizontal wind turbine of the prior art.
  • Figure 2 is a perspective view depicting delineated cross sections that represent stations of one of the rotor blades of the turbine of Figure 1.
  • Figure 3 is an orthographic end view of the delineated cross sections that represent each station of the rotor blade of Figure 2.
  • Figure 4 illustrates even blade loading of a power-extracting region of the rotor blade of Figures 2 and 3.
  • Figure 5 is a graphical representation of the pressure differential per station (blade loading) represented in Figure 4.
  • Figure 6 is a front perspective view of an exemplary turbine embodiment of the present disclosure.
  • Figure 7 is a cross section of the turbine represented in Figure 6.
  • Figure 8 is a perspective view depicting delineated cross sections that represent the stations of one of the rotor blades of the turbine of Figures 6 and 7.
  • Figure 9 is an orthographic end view of the delineated cross sections that represent each station of the rotor blade of Figure 8.
  • Figure 10 illustrates uneven blade loading of the rotor blade of Figures 8 and 9.
  • Figure 11 is a graphical representation of the pressure differential per station (blade loading) represented in Figure 10.
  • Figures 12-14 are views of further exemplary shrouded turbine embodiments of the present disclosure.
  • a value modified by the term “about” or the term “substantially” should be interpreted as disclosing a range of values proximal to the value accounting for at least the degree of error related to the value, for example, based on design/manufacture tolerances and/or measurement errors affected the value.
  • Turbines may be used to extract energy from a variety of suitable fluids such as air (e.g. , wind turbines) and water (e.g., hydro turbines), e.g., to generate electricity.
  • suitable fluids such as air (e.g. , wind turbines) and water (e.g., hydro turbines), e.g., to generate electricity.
  • suitable fluids such as air (e.g. , wind turbines) and water (e.g., hydro turbines), e.g., to generate electricity.
  • suitable fluids such as air (e.g. , wind turbines) and water (e.g., hydro turbines), e.g., to generate electricity.
  • a Mixer-Ejector Turbine provides an improved means of extracting power from flowing fluid.
  • a primary shroud contains a rotor which extracts power from a primary fluid stream.
  • a mixer-ejector pump is included that ingests bypass for use in energizing the primary fluid flow. This mixer-ejector pump may promote turbulent mixing of the aforementioned two fluid streams. This mixing enhances the power extraction from the MET system by increasing the amount of fluid flow through the system, increasing the velocity at the rotor plane for more power availability, and reducing the pressure on down-wind side of the rotor plane and energizing the rotor wake.
  • the aerodynamic principles of a MET are not restricted to a specific fluid, and may apply to any fluid, defined as any liquid, gas or combination thereof and therefore includes water as well as air.
  • the aerodynamic principles of a mixer ejector wind turbine apply to hydrodynamic principles in a mixer ejector water turbine.
  • Exemplary rotors may include a conventional propeller-like rotor, a rotor/stator assembly, a multi-segment propeller-like rotor, or any type of rotor understood by one skilled in the art.
  • a rotor may be associated with a turbine shroud, such as described herein, and may include one or more rotor blades, for example, one or more unevenly loaded rotor blades, such as described herein, attached to a rotational shaft or hub.
  • blade is not intended to be limiting in scope and shall be deemed to include all aspects of suitable blades, including those having multiple associated blade segments.
  • the leading edge of a turbine blade and/or the leading edge of a turbine shroud may be considered the front of the turbine.
  • the trailing edge of a turbine blade and/or the trailing edge of an ejector shroud may be considered the rear of the turbine.
  • a first component of the turbine located closer to the front of the turbine may be considered "upstream” of a second component located closer to the rear of the turbine. Put another way, the second component is "downstream" of the first component.
  • the present disclosure relates to a turbine for extracting power from a non-uniform flow velocity.
  • the turbine may be configured for affecting the non-uniform flow velocity in the fluid (for example, the turbine may be a MET including a turbine shroud that is in close proximity to or surrounds a rotor and an ejector shroud that is in close proximity to or surrounds the exit of the turbine shroud).
  • the present disclosure relates to the design and implementation (for example, in a shrouded turbine) of unevenly loaded rotor blade(s) .
  • the tip to hub variation in power extracted per mass flow rate is between 40% and 90%, or in other words, the area toward the tip region of the rotor extracts between 40% and 90% more power per mass flow rate than the area toward the root region at the hub of the rotor blade.
  • the mass-average total pressure drop from the upstream area to the downstream area may remain the same.
  • FIG. 1 is a perspective view of an embodiment of a conventional HAWT 100 of the prior art.
  • the HAWT 100 includes rotor blades 112 that are joined at a central hub 141 and rotate about a central axis 105.
  • the hub is joined to a shaft that is co-axial with the hub and with the nacelle 150.
  • the nacelle 150 houses electrical generation equipment (not shown).
  • the rotor plane is represented by the dotted line 115.
  • FIG. 2-4 an exemplary rotor blade 112, (e.g., for the HAWT 100 of Figure 1) is shown.
  • Cross sections 160, 162, 164... 180 are delineated at different radial positions relative to the axis of rotation (e.g., relative to the central axis of Figure 1) along a central blade axis 107.
  • Each cross section 160, 162, 164. . . 180 represents a station along the blade 112 and defines an airfoil.
  • each airfoil may be characterized based on the length and pitch of a cord between the leading and trailing edges of the airfoil (note this is merely an illustrative embodiment, however, and any number of parameters relating to the shape and/or pitch of the airfoil may be identified and used to characterize the airfoil).
  • Cross section 160 defines chord 161.
  • cross section 180 defines chord 181.
  • each chord has a length and a pitch as seen in the length and relative pitch angle between chords 161 and 181.
  • the chord length and pitch of each cross section affects the loading on the blade at the corresponding station.
  • Figure 4 depicts blade loading (Ap) across different regions of the blade 112. Blade loading (Ap) is illustrated using horizontal hash markings wherein the spacing between the hash markings is inversely proportional to blade loading. As depicted in Figure 4,
  • conventional HAWT blades are designed to have even blade loading at each station across a power-extracting region of the blade 112 when operating in a fluid stream.
  • the blade 112 includes two non-power-extracting regions proximal to the root and tip of the blade (see cross sections 160 and 180, respectively).
  • the non-power extracting regions are identifiable by the sudden minimal blade loading represented in Figure 4 by sparse horizontal hash marking at the root and tip of the blade 112.
  • Figure 5 depicts a graphical representation of blade loading per station as represented in Figure 4 for blade 112. As noted with respect to Figure 5 even blade loading is evident for stations in a power-extracting region of the blade 112 (see, e.g., cross sections 162, 164, 166 and 178). Minimal blade loading is evident for stations in non-energy extracting regions of the blade 112 near the root and tip (see, e.g., cross- sections 160 and 180, respectively). The position of the cross sections 160, 162, 164. . .180 along the axis 107 is represented along the vertical axis of the graph.
  • Blade loading characterized by a pressure differential (Ap) in pounds per square foot (psf) is represented along the horizontal axis of the graph.
  • the vertical alignment cross sections from the power-extracting region of the blade 112 represents substantially identical, or even, blade loading.
  • FIG. 6 is a perspective view of an exemplary embodiment of a shrouded turbine 200 of the present disclosure.
  • Figure 7 is a cross-sectional view of the shrouded turbine of Figure 6.
  • the shrouded turbine 200 includes a turbine shroud 210, a nacelle body 250, a rotor 239, and an ejector shroud 220.
  • the turbine shroud 210 includes a front end 212, also known as an inlet end or a leading edge.
  • the turbine shroud 210 also includes a rear end 216, also known as an exhaust end or trailing edge.
  • the ejector shroud 220 includes a front end, inlet end or leading edge 222, and a rear end, exhaust end, or trailing edge 224. Support members 206 are shown connecting the turbine shroud 210 to the ejector shroud 220.
  • the rotor 239 is operatively coupled to the nacelle body 250.
  • the rotor 239 includes a central hub 241 at the proximal end of one or more rotor blades 240 and defines a rotor plane where the fluid flow intersects the blades 240.
  • the central hub 241 is rotationally engaged with the nacelle body 250.
  • the nacelle body 250 and the turbine shroud 210 are supported by a tower 202.
  • the rotor 239, turbine shroud 210, and ejector shroud 220 are coaxial with each other, i.e. they share a common central axis 205.
  • the turbine shroud 210 has the cross-sectional shape of an airfoil with a leading edge 212 and the suction side (i.e. low pressure side) on the interior of the shroud.
  • the rear end 216 of the turbine shroud also has mixing lobes including rotor flow (low energy) mixing lobes 215 and bypass flow (high energy) mixing lobes 217.
  • the mixing lobes extend downstream beyond the rotor blades 240.
  • the trailing edge 216 of the turbine shroud is shaped to form two different sets of mixing lobes.
  • High energy mixing lobes 217 extend inwardly towards the central axis 205 of the mixer shroud.
  • Low energy mixing lobes 215 extend outwardly away from the central axis 205.
  • An opening in the sidewall 219 between the low energy lobe 215 and the high energy mixing lobe 217 increases mixing between high and low energy streams.
  • a mixer-ejector pump is formed by the ejector shroud 220 in fluid communication with the ring of high energy mixing lobes 217 and low energy mixing lobes 215 on the turbine shroud 210.
  • the mixing lobes 217 extend downstream toward the inlet end 222 of the ejector shroud 220.
  • This mixer-ejector pump provides the means for increased operational efficiency.
  • the area of higher velocity fluid flow is generally depicted by the shaded area 245 ( Figure 7).
  • rotor blades in a mixer-ejector turbine may be designed appropriately to take advantage of the energy transfer as a result of the mixing between the bypass flow and the rotor wake flow.
  • FIG. 8-10 an example rotor blade 240 (e.g., for the mixer- ejector turbine 200 of Figures 6-7), is shown.
  • the blade 240 advantageously includes a power-extracting region adapted for radially- varied (relative to the axis of rotation) power extraction per mass flow rate.
  • Cross sections 260, 262, 264. . . 284 are delineated at different radial positions relative to the axis of rotation (e.g., relative to axis 205 of Figures 6-7) along the central axis 207 of the blade.
  • each airfoil may be characterized based on the length and pitch of a cord between the leading and trailing edges of the airfoil (note this is merely an illustrative embodiment, however, and any number of parameters relating to the shape and/or pitch of the airfoil may be identified and used to characterize the airfoil).
  • Cross section 260 defines chord 261.
  • cross section 284 defines chord 283.
  • the rotor blade 240 may be constructed and/or modeled using multiple blade segments, e.g., such as defined between cross sections, wherein each blade segment actually has or is assumed to have a constant airfoil shape and pitch (e.g., a constant chord length and chord pitch).
  • the airfoil shape and/or pitch of one segment need not be contiguous with the airfoil shape and/or pitch of an adjacent segment.
  • the rotor blade 240 may be constructed and/or modeled as a contiguous structure, e.g., wherein the shape and pitch of the airfoil changes contiguously with respect to radial- position.
  • the rotor blade 240 may be modeled as an infinite number of blade segments of a width (dr) approaching zero. Analysis of forces and/or structural parameters can be achieved by integrating over a length of the blade 240 (0 to R).
  • each chord has a length and a pitch as seen in the length and relative pitch angle between chords 261 and 283.
  • Airfoil characteristics such as the chord length and pitch of each cross section affect the loading on the blade at the corresponding station.
  • the pitch and/or shape of the airfoil at a first cross section e.g., cross section 284, is configured, so that the power extraction per mass flow rate of the blade 240 at that first cross section is different than the power extraction per mass flow rate of the blade 240 at a second cross section, e.g., cross section 260.
  • Blade 240 is advantageously configured to take advantage of the non-uniform flow profile resulting from the mixer-ejector pump of the turbine 200 of Figures 6-7 with greater loading toward the tip to take advantage of the region of greater fluid flow velocity (shaded area 245 of Figure 7).
  • Blade 240 illustrates how a power-extracting region of an unevenly loaded blade may optimized for an expected relative flow velocity between fluid flow at a first radial position and fluid flow at a second radial position.
  • the power-extracting region of an unevenly loaded blade may optimized based on optimal lift/drag ratios for each radial position such as a maximal lift/drag ratio prior to stall or prior to a selected safety threshold.
  • relative flow velocity between two radial positions may be related, for example, proportional to relative power extraction per mass flow rate between the two radial positions.
  • FIG 10 depicts blade loading (Ap) across different regions of the blade 240.
  • Blade loading (Ap) is illustrated using horizontal hash markings wherein the spacing between the hash markings is inversely proportional to blade loading.
  • blade 240 is designed to have uneven blade loading at each station across a power-extracting region of the blade 240 when operating in the fluid stream of turbine 200 of Figures 6-7. More particularly, blade 240 is configured to exhibit greater loading toward the tip to take advantage of the region of greater fluid flow velocity.
  • the power-extracting region includes portions of the blade from cross section 260 to cross section 284, e.g., there are no non-power extracting regions toward the tip or root.
  • Figure 11 depicts a graphical representation of blade loading per station as represented in Figure 10 for blade 240.
  • uneven blade loading is evident for stations of the blade 240 (see, e.g., the gradual decrease in blade loading from station 284 to station 260).
  • the position of cross-sections 260, 262, 264. . .284 along the central blade axis 207 is represented along the vertical axis of the graph.
  • Blade loading characterized by a pressure differential (Ap) in pounds per square foot (psf) is represented along the horizontal axis of the graph.
  • the load at a station that represents the blade tip is between 20% and 45% greater than the load at a mean section (cross section 270), similarly, the load at a station that represents the blade root (cross section 260) is 20% to 45% lower than that of the mean section (cross section 270).
  • mixer/ejector turbine 200 of Figures 6-7 is only one example of a shrouded turbine which may be used in accordance with the apparatus, systems and methods of the present disclosure to produce a non-uniform flow profile across a rotor plane.
  • shrouded turbines e.g., with or without an ejector shroud and/or with or without mixing lobes may also be used instead to produce non-uniform flow profile across a rotor plane. See, for example, Figures 12-14, depicting further exemplary shrouded turbine embodiments capable of producing a nonuniform flow profile across a rotor plane.
  • Figure 12 is a perspective view of a further example embodiment of a shrouded turbine 300 including a turbine shroud 310 characterized by a ringed airfoil. Unlike the turbine 200 of Figures 6-7, turbine 300 does not include an ejector shroud. Turbine 300 also includes a nacelle body 350 and a rotor 339 including a plurality of rotor blades 340. Unlike the turbine 200 of Figures 6-7, turbine 300 in the embodiment of Figure 12 does not include an ejector shroud. The turbine shroud 310
  • Turbine shroud 310 further includes mixing elements 315 and 317.
  • Mixing elements 315 and 317 include inward turning mixing elements 317 which turn inward toward a central axis 305 and outward turning mixing elements 315 which turn outward from the central axis 305.
  • the turbine shroud 310 includes a front end 312 also known as an inlet end or a leading edge.
  • Mixing elements 315 and 317 include a rear end 316, also known as an exhaust end or trailing edge.
  • Support structures 306 are engaged at the proximal end, with the nacelle body 350 and at the distal end with the turbine shroud 310.
  • the rotor, nacelle body 350, and turbine shroud 310 are concentric about a common axis 305 (which is the axis of rotation for the rotor 339) and are supported by a tower structure 302.
  • FIG. 13 depicts a cross-sectional view of a further example embodiment of a shrouded turbine 400.
  • Turbine 400 includes a shrouded turbine 410 characterized by a ringed airfoil.
  • Turbine 400 also includes a nacelle body 450 and a rotor 439 including a plurality of rotor blades 440. Similar to the turbine 300 of Figure 12, the turbine 400 depicted in Figure 13 does not include an ejector shroud.
  • the turbine shroud 410 advantageously induces a non-uniform flow profile across a rotor plane 409. Unlike the turbine shroud 310 in Figure 12, the turbine shroud 410 in the embodiment of
  • the turbine shroud 410 includes a front end 412 also known as an inlet end or a leading edge and a rear end 416, also known as an exhaust end or trailing edge.
  • Support structures 406 are engaged at a proximal end with the nacelle body 450 and at the distal end with the turbine shroud 410.
  • the rotor 439, nacelle body 450, and turbine shroud 410 are concentric about a common axis 405 (which is the axis of rotation for the rotor 439) and are supported by a tower structure 402.
  • FIG. 14 depicts a cross section view of a further example embodiment of a shrouded turbine 500.
  • Turbine 500 includes a shrouded turbine 510 characterized by a ringed airfoil.
  • Turbine 500 also includes a nacelle body 550 and a rotor 539 including a plurality of rotor blades 540. Similar to the turbines 300 and 400 of Figures 12-13, the turbine 500 depicted in Figure 14 does not include an ejector shroud.
  • the turbine shroud 510 advantageously induces a non-uniform flow profile across a rotor plane 509.
  • turbine shroud 510 advantageously defines a plurality of passages 519 extending from the outer surface to the inner surface of the turbine shroud 510. Passages 519 act as bypass ducts that providing mixing between a bypass flow 503 and the fluid flow through the turbine 500 down-stream from the rotor plane
  • 510 includes a front end 512 also known as an inlet end or a leading edge and a rear end 516, also known as an exhaust end or trailing edge.
  • Support structures 506 are engaged at a proximal end with the nacelle body 550 and at the distal end with the turbine shroud 510.
  • the rotor 539, nacelle body 550, and turbine shroud 510 are concentric about a common axis 505 (which is the axis of rotation for the rotor) and are supported by a tower structure 502.
  • a turbine shroud may not be the only mechanism in a turbine for inducing a non-uniform flow profile across a rotor plane of a turbine. Indeed, any appropriate mechanism may be used to manipulate fluid flow instead of or in addition to a turbine shroud.

Abstract

L'invention concerne une aube de rotor de turbine irrégulièrement chargée, l'aube comprenant une région d'extraction d'énergie conçue pour effectuer une extraction d'énergie par débit massique qui varie dans la direction radiale (par rapport à l'axe de rotation). Dans une première position radiale, le pas et/ou la forme d'un profil aérodynamique peuvent être configurés de telle sorte que l'extraction d'énergie par débit massique dans la première position radiale est différente de l'extraction d'énergie par débit massique dans une seconde position radiale. De cette façon, la région d'extraction d'énergie peut être avantageusement configurée pour tirer avantage d'un profil de flux non uniforme à travers d'un plan du rotor comme celui qui peut être induit lorsqu'on utilise une turbine carénée.
PCT/US2012/039644 2011-05-27 2012-05-25 Turbine à aubes de rotor irrégulièrement chargées WO2012166625A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CA2834595A CA2834595A1 (fr) 2011-05-27 2012-05-25 Turbine a aubes de rotor irregulierement chargees
EP12726977.7A EP2715119A1 (fr) 2011-05-27 2012-05-25 Turbine à aubes de rotor irrégulièrement chargées

Applications Claiming Priority (2)

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US201161490841P 2011-05-27 2011-05-27
US61/490,841 2011-05-27

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WO2012166625A1 true WO2012166625A1 (fr) 2012-12-06

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PCT/US2012/039660 WO2012166632A1 (fr) 2011-05-27 2012-05-25 Aubes de turbine à charge d'aube mixte

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US (2) US20120301283A1 (fr)
EP (2) EP2715119A1 (fr)
CN (1) CN103597205A (fr)
CA (2) CA2834595A1 (fr)
WO (2) WO2012166625A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8461713B2 (en) * 2009-06-22 2013-06-11 Johann Quincy Sammy Adaptive control ducted compound wind turbine
FR3003311A1 (fr) * 2013-03-12 2014-09-19 Sauval Claude Rene Turbine eolienne etagee a carenage venturi multiflux et turbine a gaz
GB2539237B (en) 2015-06-10 2020-12-09 Equinor Asa Rotor blade shaped to enhance wake diffusion
EP3179093A1 (fr) * 2015-12-08 2017-06-14 Winfoor AB Pale de rotor pour une éolienne et un sous-élément
US11028822B2 (en) * 2018-06-19 2021-06-08 University Of Massachusetts Wind turbine airfoil structure for increasing wind farm efficiency
CN110863942B (zh) * 2019-12-23 2020-11-24 沈阳航空航天大学 用于提高风能利用率的聚能型水平轴风力机及使用方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1233178A2 (fr) * 1999-11-23 2002-08-21 Marrero O'Shanahan, Pedro M. Eolienne a acceleration de flux
WO2003029644A1 (fr) * 2001-09-21 2003-04-10 Hammerfest Strøm As Procede de conception de pales impliquant des calculs iteratifs et traitement des plans
WO2005078277A2 (fr) * 2004-02-13 2005-08-25 Aloys Wobben Pale d'une installation d'energie eolienne
WO2007107505A1 (fr) * 2006-03-21 2007-09-27 Shell Internationale Research Maatschappij B.V. Ensemble turbine et generateur
EP1978245A1 (fr) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Agencement optimisé de pales de rotor d'éolienne
US20090263244A1 (en) * 2007-03-23 2009-10-22 Presz Jr Walter M Water Turbines With Mixers And Ejectors
US20100239411A1 (en) * 2008-12-12 2010-09-23 Annette Lane Dual-mode wind machine
US8021100B2 (en) 2007-03-23 2011-09-20 Flodesign Wind Turbine Corporation Wind turbine with mixers and ejectors

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2949447C2 (de) * 1979-12-08 1982-04-01 Voith Getriebe Kg, 7920 Heidenheim Axialventilator, insbesondere zur Bodenfrostbekämpfung
US20110052400A1 (en) * 2009-08-31 2011-03-03 Sarbuland Khan Horizontal axis wind turbine (HAWT)

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1233178A2 (fr) * 1999-11-23 2002-08-21 Marrero O'Shanahan, Pedro M. Eolienne a acceleration de flux
WO2003029644A1 (fr) * 2001-09-21 2003-04-10 Hammerfest Strøm As Procede de conception de pales impliquant des calculs iteratifs et traitement des plans
WO2005078277A2 (fr) * 2004-02-13 2005-08-25 Aloys Wobben Pale d'une installation d'energie eolienne
WO2007107505A1 (fr) * 2006-03-21 2007-09-27 Shell Internationale Research Maatschappij B.V. Ensemble turbine et generateur
US20090263244A1 (en) * 2007-03-23 2009-10-22 Presz Jr Walter M Water Turbines With Mixers And Ejectors
US8021100B2 (en) 2007-03-23 2011-09-20 Flodesign Wind Turbine Corporation Wind turbine with mixers and ejectors
EP1978245A1 (fr) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Agencement optimisé de pales de rotor d'éolienne
US20100239411A1 (en) * 2008-12-12 2010-09-23 Annette Lane Dual-mode wind machine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
GASCH, R.: "Windkraftanlagen", 1 January 1996, B.G. TEUBNER, Stuttgart, ISBN: 3-519-26334-3, article "5.4 Die Betsche Optimalauslegung", pages: 129 - 135, XP002681506, 236270 *
HAU ERICH: "Windkraftanlagen", 1 January 1996, SPRINGER VERLAG, Berlin, ISBN: 978-3-540-57430-9, article 5.4: "Die wichtigste Merkmale des Rotors aus aerodynamischer Sicht", pages: 91 - 118, XP008154394 *

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US20120301283A1 (en) 2012-11-29
CN103597205A (zh) 2014-02-19
CA2832984A1 (fr) 2012-12-06
WO2012166632A1 (fr) 2012-12-06
CA2834595A1 (fr) 2012-12-06
EP2715119A1 (fr) 2014-04-09
EP2715120A1 (fr) 2014-04-09
US20120315125A1 (en) 2012-12-13

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